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Drag Coefficient for given parasite drag coefficient Formula

GoDrag Coefficient for given zero-lift drag coefficient Formula

GoDrag coefficient given Drag Force Formula

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Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water. Check FAQs

C D = C D,e + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

C_D - Drag Coefficient?C_D,e - Parasite Drag coefficient?C_L - Lift Coefficient?e_oswald - Oswald Efficiency Factor?AR - Aspect Ratio of a Wing?π - Archimedes' constant?

Drag Coefficient for given parasite drag coefficient Example

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Here is how the Drag Coefficient for given parasite drag coefficient equation looks like with Values.

Here is how the Drag Coefficient for given parasite drag coefficient equation looks like with Units.

Here is how the Drag Coefficient for given parasite drag coefficient equation looks like.

29.9926 = 29.8 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

29.9926 = 29.8 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

29.9926 = 29.8 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

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Drag Coefficient for given parasite drag coefficient Solution

Follow our step by step solution on how to calculate Drag Coefficient for given parasite drag coefficient?

FIRST Step Consider the formula

C D = C D,e + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Next Step Substitute values of Variables

∴

C D = 29.8 + (\frac{{1.1}^{2}}{π \cdot 0.5 \cdot 4})

Next Step Substitute values of Constants

∴

C D = 29.8 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

Next Step Prepare to Evaluate

∴

C D = 29.8 + (\frac{{1.1}^{2}}{3.1416 \cdot 0.5 \cdot 4})

Next Step Evaluate

∴

C D = 29.9925774811412

LAST Step Rounding Answer

∴

C D = 29.9926

Drag Coefficient for given parasite drag coefficient Formula Elements

Variables

Constants

Drag Coefficient

Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

Symbol: C_D

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Drag Coefficient

Parasite Drag coefficient

The parasite Drag coefficient is defined as the combination of coefficients of form drag and skin friction drag.

Symbol: C_D,e

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Parasite Drag coefficient

Lift Coefficient

The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Oswald Efficiency Factor

The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio.

Symbol: e_oswald

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Oswald Efficiency Factor

Aspect Ratio of a Wing

The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Aspect Ratio of a Wing

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

Other Formulas to find Drag Coefficient

Go Drag Coefficient for given zero-lift drag coefficient

C D = C D,0 + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Drag coefficient given Drag Force

C D = \frac{F D}{q}

Go Coefficient of drag given drag

C D = \frac{C L \cdot F D}{W 0}

Go Drag coefficient given lift coefficient

C D = C L \cdot \frac{F D}{F L}

Other formulas in Lift and Drag Polar category

Go Coefficient of Drag due to lift

C D,i = \frac{{C L}^{2}}{π \cdot e oswald \cdot AR}

Go Parasite Drag Coefficient at zero lift

C D,0 = C D - C D,i

Go Modern Lift Equation

L = \frac{C L \cdot ρ air \cdot S \cdot {u f}^{2}}{2}

Go Lift coefficient given Lift Force

C L = \frac{F L}{q}

How to Evaluate Drag Coefficient for given parasite drag coefficient?

Drag Coefficient for given parasite drag coefficient evaluator uses Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)) to evaluate the Drag Coefficient, Drag Coefficient for given parasite drag coefficient is a dimensionless quantity that characterizes the drag of an object in a fluid environment, influenced by the parasite drag coefficient, lift coefficient, Oswald efficiency factor, and aspect ratio, providing a comprehensive measure of an object's aerodynamic performance. Drag Coefficient is denoted by C_D symbol.

How to evaluate Drag Coefficient for given parasite drag coefficient using this online evaluator? To use this online evaluator for Drag Coefficient for given parasite drag coefficient, enter Parasite Drag coefficient (C_D,e), Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a Wing (AR) and hit the calculate button.

FAQs on Drag Coefficient for given parasite drag coefficient

What is the formula to find Drag Coefficient for given parasite drag coefficient?

The formula of Drag Coefficient for given parasite drag coefficient is expressed as Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). Here is an example- 5.192577 = 29.8+((1.1^2)/(pi*0.5*4)).

How to calculate Drag Coefficient for given parasite drag coefficient?

With Parasite Drag coefficient (C_D,e), Lift Coefficient (C_L), Oswald Efficiency Factor (e_oswald) & Aspect Ratio of a Wing (AR) we can find Drag Coefficient for given parasite drag coefficient using the formula - Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)). This formula also uses Archimedes' constant .

What are the other ways to Calculate Drag Coefficient?

Here are the different ways to Calculate Drag Coefficient-

Drag Coefficient=Zero-Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))
Drag Coefficient=Drag Force/Dynamic Pressure
Drag Coefficient=(Lift Coefficient*Drag Force)/Gross Weight

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Drag Coefficient for given parasite drag coefficient Formula

​GoDrag Coefficient for given zero-lift drag coefficient Formula

​GoDrag coefficient given Drag Force Formula

Drag Coefficient for given parasite drag coefficient Example

Drag Coefficient for given parasite drag coefficient Solution

Drag Coefficient for given parasite drag coefficient Formula Elements

Other Formulas to find Drag Coefficient

Other formulas in Lift and Drag Polar category

How to Evaluate Drag Coefficient for given parasite drag coefficient?

FAQs on Drag Coefficient for given parasite drag coefficient

Variable Name

GoDrag Coefficient for given zero-lift drag coefficient Formula

GoDrag coefficient given Drag Force Formula